Engine gateway with engine data storage

ABSTRACT

An engine gateway of a gas turbine engine of an aircraft includes a communication interface configured to wirelessly communicate with an offboard system and to communicate with an engine control of the gas turbine engine, a memory system, a data storage system isolated from the memory system, and processing circuitry. The processing circuitry is configured to establish communication with the engine control on a first communication bus using system credential authentication, establish communication between the engine control and the data storage system on a second communication bus, establish wireless communication with the offboard system using system credential authentication, and provide access from the offboard system through the engine gateway, from the engine gateway through the engine control, and from the engine control to the data storage system to enable one or more updates of the data storage system by the offboard system based on service credential authentication.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application claims the benefit of priority to U.S. ProvisionalApplication No. 62/835,169 filed Apr. 17, 2019, the disclosure of whichis incorporated by reference herein in its entirety.

BACKGROUND

The subject matter disclosed herein generally relates to gas turbineengine communication systems and, more particularly, to an enginegateway with wireless communication and engine data storage for a gasturbine engine.

A control system of a gas turbine engine uses multiple configurationcontrol items, such as control software, data, trim updatable values,and the like to control operation of the gas turbine engine and monitorperformance of the gas turbine engine. Once a gas turbine engine isdeployed in the field, it can be difficult to access data capturedand/or computed by the control system and to make updates to theconfiguration control items. A gas turbine engine can be deployed in thefield for an extended service life, such as a period of decades.Computer system technology and communication technology can evolve at arapid pace adding to the challenges of interfacing with offboard systemsas the offboard technology continues to advance during the lifespan ofthe engine.

As components are replaced on an engine, a configuration history can betracked in various locations. If configuration history data ismaintained within an engine control, the configuration history data maybe lost if the engine control is swapped out.

BRIEF DESCRIPTION

According to one embodiment, an engine gateway of a gas turbine engineof an aircraft includes a communication interface configured towirelessly communicate with an offboard system and to communicate withan engine control of the gas turbine engine, a memory system, a datastorage system isolated from the memory system, and processingcircuitry. The processing circuitry is configured to establishcommunication with the engine control on a first communication bus usingsystem credential authentication, establish communication between theengine control and the data storage system on a second communicationbus, establish wireless communication with the offboard system usingsystem credential authentication, and provide access from the offboardsystem through the engine gateway, from the engine gateway through theengine control, and from the engine control to the data storage systemto enable one or more updates of the data storage system by the offboardsystem based on service credential authentication.

In addition to one or more of the features described above or below, oras an alternative, further embodiments may include where the secondcommunication bus provides electrical power from the engine control tothe data storage system.

In addition to one or more of the features described above or below, oras an alternative, further embodiments may include where the datastorage system includes a controller and one or more non-volatile memorydevices.

In addition to one or more of the features described above or below, oras an alternative, further embodiments may include where the controlleris configured to manage the one or more updates using a buffer thatenables reversion to a previous state of one or more data records basedon detecting an error condition.

In addition to one or more of the features described above or below, oras an alternative, further embodiments may include where the processingcircuitry is further configured to communicate with the controller in amaintenance mode based on determining that the engine control isdisconnected from the engine gateway, where the maintenance mode isenabled based on one or more of: a discrete input, a keycode, and aconnection between the first communication bus and the secondcommunication bus.

In addition to one or more of the features described above or below, oras an alternative, further embodiments may include where user credentialauthentication is performed in combination with system credentialauthentication and service credential authentication.

In addition to one or more of the features described above or below, oras an alternative, further embodiments may include where the enginegateway is mounted on a fan case of the gas turbine engine, and theengine gateway is physically separated from the engine control.

According to an embodiment, a method includes establishing communicationbetween an engine control of a gas turbine engine of an aircraft and anengine gateway on a first communication bus using system credentialauthentication, establishing communication between the engine controland a data storage system of the engine gateway on a secondcommunication bus, where the data storage system is isolated from amemory system of the engine gateway, and establishing wirelesscommunication between the engine gateway and an offboard system usingsystem credential authentication. The method also includes providingaccess from the offboard system through the engine gateway, from theengine gateway through the engine control, and from the engine controlto the data storage system to enable one or more updates of the datastorage system by the offboard system based on service credentialauthentication.

In addition to one or more of the features described above or below, oras an alternative, further embodiments may include receiving electricalpower on the second communication bus at the data storage system fromthe engine control.

In addition to one or more of the features described above or below, oras an alternative, further embodiments may include managing, by thecontroller, the one or more updates using a buffer that enablesreversion to a previous state of one or more data records based ondetecting an error condition.

In addition to one or more of the features described above or below, oras an alternative, further embodiments may include communicating betweenthe engine gateway and the controller in a maintenance mode based ondetermining that the engine control is disconnected from the enginegateway, where the maintenance mode is enabled based on one or more of:a discrete input, a keycode, and a connection between the firstcommunication bus and the second communication bus.

According to an embodiment, a gas turbine engine of an aircraft includesa fan section with a fan case, an engine control mounted on the fancase, and an engine gateway mounted on the fan case. The engine controlis configured to monitor and control operation of the gas turbine enginein real-time. The engine gateway includes a data storage system isolatedfrom a memory system of the engine gateway and processing circuitryconfigured to establish communication with the engine control on a firstcommunication bus using system credential authentication, establishcommunication between the engine control and the data storage system ona second communication bus, establish wireless communication with theoffboard system using system credential authentication, and provideaccess from the offboard system through the engine gateway, from theengine gateway through the engine control, and from the engine controlto the data storage system to enable one or more updates of the datastorage system by the offboard system based on service credentialauthentication.

A technical effect of the apparatus, systems and methods is achieved byincorporating communication features to provide an engine gateway withwireless communication and engine data storage as described herein.

BRIEF DESCRIPTION OF THE DRAWINGS

The following descriptions should not be considered limiting in any way.With reference to the accompanying drawings, like elements are numberedalike:

FIG. 1 is a block diagram of a system supporting wireless communicationbetween an engine and offboard systems, in accordance with an embodimentof the disclosure;

FIG. 2 is a block diagram illustrating further details of the system ofFIG. 1, in accordance with an embodiment of the disclosure;

FIG. 3 is a block diagram of configuration items of an engine control,in accordance with an embodiment of the disclosure;

FIG. 4 is a block diagram of a configuration management database of anoffboard system to track multiple engine configurations, in accordancewith an embodiment of the disclosure;

FIG. 5 is a block diagram of a buffer configuration, in accordance withan embodiment of the disclosure; and

FIG. 6 is a flow chart illustrating a method, in accordance with anembodiment of the disclosure.

DETAILED DESCRIPTION

A detailed description of one or more embodiments of the disclosedapparatus and method are presented herein by way of exemplification andnot limitation with reference to the Figures.

Referring now to the drawings, FIG. 1 illustrates a system 100supporting wireless communication between an engine gateway 102 of a gasturbine engine 104 and a plurality of offboard systems 106. The gasturbine engine 104 can be coupled to an aircraft 108, where the aircraft108 can include multiple instances of the gas turbine engine 104. Thegas turbine engine 104 can include a fan section 110, a compressorsection 112, a combustor section 114, and a turbine section 116. The fansection 110 drives air along a bypass flow path, while the compressorsection 112 drives air along a core flow path for compression and flowinto the combustor section 114 then expansion through the turbinesection 116. A fan case 118 of the fan section 110 can be covered by acowling 120 and may provide an installation surface that is cooler thanother sections 112-116 of the gas turbine engine 104.

An engine control 122 can be mounted on the fan case 118 and covered bythe cowling 120. The engine control 122 is configured to monitor andcontrol operation of the gas turbine engine 104 in real-time. In orderto transfer configuration items, such as programs and data to and fromthe engine control 122, contemporary systems typically require that thecowling 120 is opened and multiple cables of bundled wires are coupledto the engine control 122. Such a process can ensure deliberate actionsare taken in extracting data and performing updates to the enginecontrol 122; however, the process can be slow and require large lengthsof customized cables. In embodiments, the engine gateway 102, alsoreferred to as a gas turbine engine communication gateway, is configuredto establish communication with the engine control 122 and wirelesscommunication with one or more offboard systems 106 external to theaircraft 108. Similar to the engine control 122, the engine gateway 102can be mounted on the fan case 118 and covered by the cowling 120 of thegas turbine engine 104. Wireless communication can alleviate the needfor customized cables or physically opening the cowling 120 to establishcommunication with the offboard systems 106.

The offboard systems 106 can include, for example, a ground station 124,a near-wing maintenance computer 126, an access portal 130, and/or otherdevices (not depicted) that may establish one-way or two-way wirelesscommunication with the engine gateway 102. For example, a globalpositioning system (GPS) can provide one-way wireless signaling to theengine gateway 102 to assist in confirming a geographic location of thegas turbine engine 104 while the engine gateway 102 is coupled to thegas turbine engine 104. Wireless communication performed by the enginegateway 102 can be through a variety of technologies with differentranges supported. As one example, the engine gateway 102 can supportWi-Fi (e.g., radio wireless local area networking based on IEEE 802.11or other applicable standards), GPS, cellular networks, satellitecommunication, and/or other wireless communication technologies known inthe art. Wireless communication between the engine gateway 102 and theoffboard systems 106 can be direct or indirect. For instance, wirelesscommunication between the engine gateway 102 and ground station 124 maypass through one or more network interface components 128, such as arepeater, while wireless communication between the engine gateway 102and the near-wing maintenance computer 126 may be direct wirelesscommunication without any relay components.

The ground station 124 can enable communication with a variety ofsupport systems, such as an access portal 130 that enables authorizedusers to access data, initiate tests, configure software, and performother actions with respect to the engine control 122, where the enginegateway 102 acts as a secure gateway to limit access and interactionswith the engine control 122. As another example, the ground station 124can communicate with a notification system 132, which may triggeralerts, text messages, e-mails, and the like to authorized recipientsregarding operational status of the gas turbine engine 104. Thenear-wing maintenance computer 126 may provide an authorized user withlimited authority a capability to query the engine gateway 102 for faultdata, test parameters, and other such information. In some embodiments,the near-wing maintenance computer 126 can be authorized with limitedauthority to make updates to select configuration parameters, softwareexecutable or data collection parameters of the engine gateway 102.

FIG. 2 is a block diagram illustrating further details of the system 100of FIG. 1, in accordance with an embodiment of the disclosure. Theengine control 122 can control effectors 202 of the gas turbine engine104 by generating one or more effector commands 204. Examples ofeffectors 202 can include one or more motors, solenoids, valves, relays,pumps, heaters, and/or other such actuation control components. Aplurality of sensors 206 can capture state data associated with the gasturbine engine 104 and provide sensed values 208 as feedback to theengine control 122 to enable closed-loop control of the gas turbineengine 104 according to one or more control laws. Examples of thesensors 206 can include one or more temperature sensors, pressuresensors, strain gauges, speed sensors, accelerometers, lube sensors, andthe like.

The engine control 122 can be a full authority digital engine controlthat includes processing circuitry 210 and a memory system 212configured to store a plurality of configuration items, where at leastone of the configuration items includes a sequence of the computerexecutable instructions for execution by the processing circuitry 210.Other types of configuration items can include but are not limited todata, such as constants, configurable data, and/or fault data. Examplesof computer executable instructions can include boot software, operatingsystem software, and/or application software. The executableinstructions may be stored or organized in any manner and at any levelof abstraction, such as in connection with controlling and/or monitoringoperation of the gas turbine engine 104. The processing circuitry 210can be any type or combination of central processing unit (CPU),including one or more of: a microprocessor, a digital signal processor(DSP), a microcontroller, an application specific integrated circuit(ASIC), a field programmable gate array (FPGA), or the like. Also, inembodiments, the memory system 212 may include volatile memory, such asrandom access memory (RAM), and non-volatile memory, such as Flashmemory, read only memory (ROM), and/or other electronic, optical,magnetic, or any other computer readable medium onto which is storeddata and algorithms in a non-transitory form.

The engine control 122 can also include one or more of an input/outputinterface 214, a communication interface 216, and/or other elements (notdepicted). The input/output interface 214 can include support circuitryfor interfacing with the effectors 202 and sensors 206, such as filters,amplifiers, digital-to-analog converters, analog-to-digital converters,and other such circuits to support digital and/or analog interfaces.Further, the input/output interface 214 can receive or output signalsto/from other sources. The communication interface 216 can becommunicatively coupled to the engine gateway 102. The communicationinterface 216 may also communicate with an aircraft bus 218 of theaircraft 108 of FIG. 1. The aircraft bus 218 may provide aircraft-levelparameters and commands that are used by the engine control 122 tocontrol the gas turbine engine 104 in real-time.

Similar to the engine control 122, the engine gateway 102 can includeprocessing circuitry 220, a memory system 222, an input/output interface224, and a communication interface 226. The processing circuitry 220 canbe any type or combination of central processing unit (CPU), includingone or more of: a microprocessor, a digital signal processor (DSP), amicrocontroller, an application specific integrated circuit (ASIC), afield programmable gate array (FPGA), or the like. Also, in embodiments,the memory system 222 may include volatile memory, such as random accessmemory (RAM), and non-volatile memory, such as Flash memory, read onlymemory (ROM), a hard disk drive, and/or other electronic, optical,magnetic, or any other computer readable medium onto which is storeddata and algorithms in a non-transitory form. The engine gateway 102 canalso include an internal sensor system 228. The internal sensor system228 can include, for example, one or more accelerometers, gyroscopes,barometers, a magnetometer (e.g., a compass), and other such sensors.Further, the engine gateway 102 can include other devices, such as a GPSreceiver 229. The input/output interface 224 can process data collectedfrom the internal sensors 228 and condition the data in a format usableby the processing circuitry 220. The communication interface 226 caninterface with one or more antennas 230, which may be integrated withthe engine gateway 102 or located remotely from the engine gateway 102,e.g., a shark-fin antenna mounted under or on the cowling 120 of FIG. 1.Although depicted separately in FIGS. 1 and 2, in some embodiments theengine control 122 and communication adapter 102 can be combined, forinstance, where the communication adapter 102 is a module or processingcore within the engine control 122.

The engine gateway 102 can act as a secure communication gateway withrespect to the offboard systems 106. For example, the offboard systems106 can request to load new/updated configuration items to the memorysystem 212 of the engine control 122 through the engine gateway 102. Thecommunication interface 216 of the engine control 122 can interface tothe communication interface 226 of the engine gateway 102 through awired, optical, or magnetic coupling. The communication interface 226can communicate wirelessly through one or more antennas 230 to theoffboard systems 106. The communication interface 226 may also haveaccess to receive data directly from the aircraft bus 218 in someembodiments. In alternate embodiments, the engine gateway 102 can send arequest to the engine control 122 to provide aircraft parametersreceived via the aircraft bus 218 and/or engine parameters computed bythe engine control 122.

Communication between the engine control 122 and the engine gateway 102can be divided between multiple busses. For example, a firstcommunication bus 232 can enable secure data exchange between the enginecontrol 122 and the engine gateway 102 to support updates/inspection ofthe contents of the memory system 212, parameter monitoring, and othersuch communication. A second communication bus 234 can supportinterfacing the engine control 122 with a data storage system 236 of theengine gateway 102. The data storage system 236 can be isolated (e.g.,physically and electrically) from the memory system 222 of the enginegateway 102. The data storage system 236 can include a controller 238(e.g., a microcontroller) and one or more non-volatile memory devices240. Separating the data storage system 236 physically from the enginecontrol 122 can provide an ability to store configuration data on thegas turbine engine 104 including, for instance, a list of maintenancebulletins implemented on the specific instance of the gas turbine engine104 to which the engine gateway 102 is attached. If the engine control122 needs to be upgraded or replaced, the configuration data stored inthe data storage system 236 remains available to the replacement versionof the engine control 122. Further, data captured in the data storagesystem 236 can be periodically synchronized with one or more offboardsystems 106.

In the example of FIG. 2, the data storage system 236 can act as anextension of the memory system 212 of the engine control 122. Thenon-volatile memory devices 240 may store fault data, trim values,service records, and other types of records associated with theconfiguration and operation of the gas turbine engine 104. Keeping thedata storage system 236 isolated from the memory system 222 andprocessing circuitry 220 of the engine gateway 102 can prevent a risk ofinstructions executing on the engine gateway 102 from corrupting thecontents of the data storage system 236. Thus, software developed forexecution on the processing circuitry 220 may be of a lower level ofcriticality, requiring less development burden than software executed onthe processing circuitry 210 of the engine control 122 and thecontroller 238. To enhance isolation, the second communication bus 234can include electric power provided by the engine control 122. Thus, thedata storage system 236 is not influenced by power interruptions withinthe engine gateway 102. Further, elements of the engine gateway 102 maybe depowered during certain operating modes, for instance, to limit theuse of wireless communication, while the data storage system 236 canremain separately powered by the engine control 122.

In some embodiments, there may be operating modes, such as a maintenancemode, where the data storage system 236 is accessible by the processingcircuitry 220. Such operating modes can be limited, for instance, toconditions where the engine control 122 is not connected to the enginegateway 102. As one example, a portion of the first communication bus232 can be looped back to the second communication bus 234 when theengine control 122 is disconnected. Other approaches to maintenance modecan include the use of discrete input to the engine gateway 102,keycodes (e.g., predetermined authorization codes) which may be writtento particular addresses in the engine gateway 102, and/or othertechniques. The maintenance mode may limit access to the non-volatilememory devices 240 as read-only or require particular conditions and/orcredential verification to authorize write updates to the non-volatilememory devices 240.

The engine gateway 102 can manage credentials and user authentication tolimit access of the memory system 212 of the engine control 122. Userauthentication can be defined for particular users or classes of users,such as equipment-owner users, maintenance technicians, engineeringusers, and the like. For example, a maintenance technician may haveauthority to adjust trimmable constants or reprogram certain regions ofthe memory system 212. An engineering user may have authority toreprogram an operating system, boot program code, or applicationsoftware in the memory system 212, in addition to having permissions ofthe maintenance technician and the equipment-owner user. If userauthentication fails, for instance, by user credentials not beingrecognized with respect to user authentication data, then the enginegateway 102 can block access of the offboard systems 106 from readingfrom or writing to the memory system 212.

Configuration items received for the engine control 122 and/or theengine gateway 102 may be encrypted using various cryptographic methodsto further enhance security. For example, the engine gateway 102 canapply a cryptographic algorithm using one or more parameters receivedand cryptographic information to decrypt an encrypted configurationitem. A combination of transmitted and stored cryptographic informationcan be used together for decryption based on ‘shared secrets’ such thatnot all of the information is sent from the offboard systems 106 norstored completely within the engine gateway 102. After decryption,authenticity of the configuration item can be verified using, forexample, a digital signature of the configuration item. The resultingfile can be a decrypted and authenticated configuration item, which maybe temporarily stored in memory system 222 or otherwise buffered duringauthentication and passed to the engine control 122 upon authentication.Updates targeted for the data storage system 236 can be wirelesslytransmitted upon credential authorization from the offboard system 106to the engine gateway 102, communicated from the engine gateway 102 tothe engine control 122 on the first communication bus 232, andcommunicated from the engine control 122 to the data storage system 236on the second communication bus 234. The engine control 122 may alsoperform a credential authorization check prior to allowing updaterequests to flow from the engine control 122 to the data storage system236.

Separating the engine gateway 102 from the engine control 122 can enablethe engine gateway 102 and the engine control 122 to have differentexpected service life durations. For example, to stay compatible withchanges in wireless communication technologies used by the offboardsystems 106, the engine gateway 102 may be upgraded at a faster intervalthan the engine control 122. The engine gateway 102 can have a lowerprocessing and storage capacity than the engine control 122 to reducepower requirements, weight, and other costs associated with the enginegateway 102. Since the engine gateway 102 does not actively control thegas turbine engine 104, development cycles may be reduced as compared toimplementing flight critical control algorithms and hardware of theengine control 122. The data storage system 236 can be modularized(e.g., aboard, card, etc.) within a housing of the engine gateway 102 toenable swapping out or upgrading of the data storage system 236separately from other components of the engine gateway 102.

FIG. 3 is a block diagram of configuration items 300 of the enginecontrol 122 of FIG. 1, in accordance with an embodiment of thedisclosure. The configuration items 300 can include one or more of aboot control 310, identification data 312, an operating system 314, anapplication 316, constant data 318, and/or configurable data 320.Further, there can be multiple instances of the configuration items 300,such as multiple instances of the application 316, constant data 318,configurable data 320, and/or other items. The configuration items 300can have different levels of criticality and authentication required.The boot control 310 can manage the loading and/or initialization ofother configuration items 300. The identification data 312 can define anumber of configuration identifiers to confirm items such as an engineserial number 322, an engine control serial number 324, an enginecontrol configuration version 326, and other such identifiers. Theoperating system 314 can provide scheduling and support for one or moreapplications 316 to interface with various hardware elements of theengine control 122 of FIG. 1. One or more applications 316 that useconstant data 318 and/or configurable data 320 can be invoked by theoperating system 314. The application 316 can be, for example,configured to control operation of the gas turbine engine 104 of FIG. 1.The configurable data 320 can include adjustable parameters to tunemonitoring performance and control performance of the engine control122, such as engine control trim data 328, fault limit data 330, engineconfiguration data 332 and other such configurable data. In embodiments,a subset of the configuration items 300 can be stored in memory devicesof the memory system 212 of FIG. 2 that are internal or external to theengine control 122. For example, the memory system 212 can includesupplemental data storage, such as a data storage unit or programmingplug to store configuration information, such as the identification data312 and/or the configurable data 320. Supplemental data storage can beaccessed through an alternate memory interface, such as a serialinterface of the engine control 122 rather than a primary memory bus ofthe engine control 122 that may be used to access executableinstructions of the configuration items 300 and/or various types ofdata.

Portions of the configuration items 300 may be stored within the datastorage system 236 of FIG. 2. For example, identification data 312 andconfigurable data 320 may be stored in the data storage system 236 alongwith other types of records. The boot control 310 and/or operatingsystem 314 can establish security protocols to reduce the risk ofexternal threats from making unauthorized accesses or updates to theconfiguration items 300 and/or other items.

FIG. 4 is a block diagram of a configuration management database 400 ofan offboard system 106 of FIG. 1 to track multiple engineconfigurations, in accordance with an embodiment of the disclosure. Forexample, the configuration management database 400 can be stored at oraccessible by the ground station 124 of FIG. 1 to track and verify theconfiguration of multiple instances of the gas turbine engine 104 ofFIG. 1 and/or changes to a specific instance of the gas turbine engine104 over a period of time. The configuration management database 400 caninclude, for example, a plurality of configuration records 402 thatcorrelate data such as engine build identifier 404, configuration data406, and log filed 408. The engine build identifier 404 can identifyspecific engine configurations and the configuration data 406 caninclude detailed data and software configuration items. For instance,the configuration data 406 may include copies or links to one or more ofthe configuration items 300 of FIG. 3 associated with an instance orgroup of gas turbine engines 104. The log files 408 can include dataextracted from the engine gateway 102 of FIG. 1, which may include datalocally collected by the engine gateway 102, the engine control 122 ofFIG. 1, the data storage system 236, and/or the aircraft bus 218 of FIG.2. The configuration data 406 and log files 408 may be access restrictedand incorporate various security features, such as authenticationrequirements, encryption, digital signatures, and the like.

FIG. 5 is a block diagram of a configuration of a buffer 500 that can beused to manage updates to the non-volatile memory devices 240 of thedata storage system 236 of FIG. 2. The buffer 500 can be implemented asa ping-pong buffer within the non-volatile memory devices 240 to storeboth existing data records 502 and data record updates 504. Thus, if anerror occurs during an update sequence of a plurality of records, thedata storage system 236 is not left in a corrupted state. The existingdata records 502 enable reversion to a previous state of one or moredata records based on detecting an error condition during a writingprocess of the data record updates 504.

Referring now to FIG. 6 with continued reference to FIGS. 1-5, FIG. 6 isa flow chart illustrating a method 600 for using the engine gateway 102of FIG. 1, in accordance with an embodiment. The method 600 may beperformed, for example, by the engine gateway 102 in conjunction withthe engine control 122 of FIG. 1 and at least one of the offboardsystems 106 of FIG. 1.

At block 602, the engine gateway 102 can establish communication withthe engine control 122 on a first communication bus 232 using systemcredential authentication. At block 604, the engine gateway 102 canestablish communication between the engine control 122 and the datastorage system 236 on a second communication bus 234. The secondcommunication bus 234 can provide electrical power from the enginecontrol 122 to the data storage system 236. The engine gateway 102 canbe mounted on a fan case 118 of the gas turbine engine 104, and theengine gateway 102 can be physically separated from the engine control122. The length of physical separation can impact the types ofcommunication buses that work in a potentially high-noise environment.For example, an inter-integrated circuit (I²C) bus may not be a viableoption due to the physical separation and potential induced noise onsignals between the engine gateway 102 and the engine control 122.Examples of bus variations can include Ethernet, CAN, and/or otherstandard or custom solutions.

At block 606, the engine gateway 102 can establish wirelesscommunication with one of the offboard systems 106 using systemcredential authentication. There can be multiple levels of credentialauthentication to verify that a user or system is authorized toestablish communication and access. Authentication may include verifyinga shared secret or other credential between the offboard system 106, theengine gateway 102, and/or the engine control 122. Further, servicecredential authentication can be used to verify a level of accessgranted to update specific portions of the memory system 212 of theengine control 122 and the data storage system 236. Service credentialauthorization can ensure that only authorized services such asinspection/monitoring or loading/modifying are allowed. Thus, in atiered authorization approach, a user credential authorization can becombined with a system credential authorization and a service credentialauthorization as a type of “combination lock” access constraint forenhanced security.

At block 608, the engine gateway 102 can provide access from theoffboard system 106 through the engine gateway 102, from the enginegateway 102 through the engine control 122, and from the engine control122 to the data storage system 236 to enable one or more updates of thedata storage system 236 by the offboard system based on servicecredential authentication. The controller 238 of the data storage system236 can be configured to manage the one or more updates using a buffer500 that enables reversion to a previous state of one or more datarecords based on detecting an error condition.

The processing circuitry 220 of the engine gateway 102 can be configuredto communicate with the controller 238 in a maintenance mode based ondetermining that the engine control 122 is disconnected from the enginegateway 102. The maintenance mode can be enabled based on one or moreof: a discrete input, a keycode, and a connection between the firstcommunication bus 232 and the second communication bus 234.

In some embodiments, the engine gateway 102 can transmit an updatecompletion confirmation of the engine control 122 and/or the datastorage system 236 from the engine gateway 102 to the offboard system106 based on a confirmation message from the engine control 122. Theconfirmation message from the engine control 122 can be sent based onvalidation of at least one digital signature associated with theconfiguration items 300 prior to updating the engine control 122. Forinstance, the configuration items 300 to be updated may be digitallysigned at the offboard system 106 and the digitally-signed configurationitems 300 can pass through the engine gateway 102 after authenticationto the engine control 122 for validation. Processing circuitry 220 ofthe engine gateway 102 can be further configured to transmit a datastate of the engine control 122 and a configuration of the enginecontrol 122 to the offboard system 106 with the update completionconfirmation. Confirmations may include a success or failure status toassist in troubleshooting unsuccessful upload attempts. The offboardsystem 106 can store results and state data, such as a load state andconfiguration, into the configuration management database 400 (e.g., aspart of the configuration data 406 and/or log files 408 associated withan engine build identifier 404).

While the above description has described the flow process of FIG. 6 ina particular order, it should be appreciated that unless otherwisespecifically required in the attached claims that the ordering of thesteps may be varied.

The term “about” is intended to include the degree of error associatedwith measurement of the particular quantity based upon the equipmentavailable at the time of filing the application.

The terminology used herein is for the purpose of describing particularembodiments only and is not intended to be limiting of the presentdisclosure. As used herein, the singular forms “a”, “an” and “the” areintended to include the plural forms as well, unless the context clearlyindicates otherwise. It will be further understood that the terms“comprises” and/or “comprising,” when used in this specification,specify the presence of stated features, integers, steps, operations,elements, and/or components, but do not preclude the presence oraddition of one or more other features, integers, steps, operations,element components, and/or groups thereof

While the present disclosure has been described with reference to anexemplary embodiment or embodiments, it will be understood by thoseskilled in the art that various changes may be made and equivalents maybe substituted for elements thereof without departing from the scope ofthe present disclosure. In addition, many modifications may be made toadapt a particular situation or material to the teachings of the presentdisclosure without departing from the essential scope thereof.Therefore, it is intended that the present disclosure not be limited tothe particular embodiment disclosed as the best mode contemplated forcarrying out this present disclosure, but that the present disclosurewill include all embodiments falling within the scope of the claims.

What is claimed is:
 1. An engine gateway of a gas turbine engine of anaircraft, the engine gateway comprising: a communication interfaceconfigured to wirelessly communicate with an offboard system and tocommunicate with an engine control of the gas turbine engine; a memorysystem; a data storage system isolated from the memory system; andprocessing circuitry configured to: establish communication with theengine control on a first communication bus using system credentialauthentication; establish communication between the engine control andthe data storage system on a second communication bus; establishwireless communication with the offboard system using system credentialauthentication; and provide access from the offboard system through theengine gateway, from the engine gateway through the engine control, andfrom the engine control to the data storage system to enable one or moreupdates of the data storage system by the offboard system based onservice credential authentication.
 2. The engine gateway of claim 1,wherein the second communication bus provides electrical power from theengine control to the data storage system.
 3. The engine gateway ofclaim 1, wherein the data storage system comprises a controller and oneor more non-volatile memory devices.
 4. The engine gateway of claim 3,wherein the controller is configured to manage the one or more updatesusing a buffer that enables reversion to a previous state of one or moredata records based on detecting an error condition.
 5. The enginegateway of claim 3, wherein the processing circuitry is furtherconfigured to: communicate with the controller in a maintenance modebased on determining that the engine control is disconnected from theengine gateway, wherein the maintenance mode is enabled based on one ormore of: a discrete input, a keycode, and a connection between the firstcommunication bus and the second communication bus.
 6. The enginegateway of claim 1, wherein user credential authentication is performedin combination with system credential authentication and servicecredential authentication.
 7. The engine gateway of claim 1, wherein theengine gateway is mounted on a fan case of the gas turbine engine, andthe engine gateway is physically separated from the engine control.
 8. Amethod comprising: establishing communication between an engine controlof a gas turbine engine of an aircraft and an engine gateway on a firstcommunication bus using system credential authentication; establishingcommunication between the engine control and a data storage system ofthe engine gateway on a second communication bus, wherein the datastorage system is isolated from a memory system of the engine gateway;establishing wireless communication between the engine gateway and anoffboard system using system credential authentication; and providingaccess from the offboard system through the engine gateway, from theengine gateway through the engine control, and from the engine controlto the data storage system to enable one or more updates of the datastorage system by the offboard system based on service credentialauthentication.
 9. The method of claim 8, further comprising: receivingelectrical power on the second communication bus at the data storagesystem from the engine control.
 10. The method of claim 8, wherein thedata storage system comprises a controller and one or more non-volatilememory devices.
 11. The method of claim 10, further comprising:managing, by the controller, the one or more updates using a buffer thatenables reversion to a previous state of one or more data records basedon detecting an error condition.
 12. The method of claim 10, whereinfurther comprising: communicating between the engine gateway and thecontroller in a maintenance mode based on determining that the enginecontrol is disconnected from the engine gateway, wherein the maintenancemode is enabled based on one or more of: a discrete input, a keycode,and a connection between the first communication bus and the secondcommunication bus.
 13. The method of claim 8, wherein user credentialauthentication is performed in combination with system credentialauthentication and service credential authentication.
 14. The method ofclaim 8, wherein the engine gateway is mounted on a fan case of the gasturbine engine, and the engine gateway is physically separated from theengine control.
 15. A gas turbine engine of an aircraft, the gas turbineengine comprising: a fan section comprising a fan case; an enginecontrol mounted on the fan case, the engine control configured tomonitor and control operation of the gas turbine engine in real-time;and an engine gateway mounted on the fan case, the engine gatewaycomprising a data storage system isolated from a memory system of theengine gateway and processing circuitry configured to establishcommunication with the engine control on a first communication bus usingsystem credential authentication, establish communication between theengine control and the data storage system on a second communicationbus, establish wireless communication with the offboard system usingsystem credential authentication, and provide access from the offboardsystem through the engine gateway, from the engine gateway through theengine control, and from the engine control to the data storage systemto enable one or more updates of the data storage system by the offboardsystem based on service credential authentication.
 16. The gas turbineengine of claim 15, wherein the second communication bus provideselectrical power from the engine control to the data storage system. 17.The gas turbine engine of claim 15, wherein the data storage systemcomprises a controller and one or more non-volatile memory devices. 18.The gas turbine engine of claim 17, wherein the controller is configuredto manage the one or more updates using a buffer that enables reversionto a previous state of one or more data records based on detecting anerror condition.
 19. The gas turbine engine of claim 17, wherein theprocessing circuitry is further configured to: communicate with thecontroller in a maintenance mode based on determining that the enginecontrol is disconnected from the engine gateway, wherein the maintenancemode is enabled based on one or more of: a discrete input, a keycode,and a connection between the first communication bus and the secondcommunication bus.
 20. The gas turbine engine of claim 15, wherein usercredential authentication is performed in combination with systemcredential authentication and service credential authentication.